(57) A gas turbine engine combustion chamber (28) comprises a primary combustion zone
(36) and a secondary combustion zone (40) downstream of the primary combustion zone
(36). A catalytic combustion zone (44) is arranged downstream of the secondary combustion
zone (40) and a homogeneous combustion zone (100) is arranged downstream of the catalytic
combustion zone (44). A pilot injector (62) supplies fuel into the primary combustion
zone (36). At least one primary premixing duct (54,56) has a plurality of primary
fuel injectors (58,60) to supply a first mixture of fuel and air into the primary
combustion zone (36). A secondary premixing duct (64) has a plurality of secondary
fuel injectors (82) to supply a second mixture of fuel and air into the secondary
combustion zone (40). A plurality of temperature sensors (102) are arranged at the
intake to the catalytic combustion zone (44) and a processor (104) controls the valves
(106,108,110) which adjust the supply of fuel the fuel injectors (58,60,62,82) to
ensure that the temperature at the intake to the catalytic combustion zone (44) remains
in a predetermined temperature range.
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